EP2730844A1 - Bardeaux de chambre de combustion d'une turbine à gaz et leur procédé fabrication - Google Patents

Bardeaux de chambre de combustion d'une turbine à gaz et leur procédé fabrication Download PDF

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Publication number
EP2730844A1
EP2730844A1 EP13191946.6A EP13191946A EP2730844A1 EP 2730844 A1 EP2730844 A1 EP 2730844A1 EP 13191946 A EP13191946 A EP 13191946A EP 2730844 A1 EP2730844 A1 EP 2730844A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
shingle
air hole
support element
mixing air
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13191946.6A
Other languages
German (de)
English (en)
Other versions
EP2730844B1 (fr
Inventor
Carsten Dr. Clemen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2730844A1 publication Critical patent/EP2730844A1/fr
Application granted granted Critical
Publication of EP2730844B1 publication Critical patent/EP2730844B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23B—TURNING; BORING
    • B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23B—TURNING; BORING
    • B23B41/00—Boring or drilling machines or devices specially adapted for particular work; Accessories specially adapted therefor
    • B23B41/14—Boring or drilling machines or devices specially adapted for particular work; Accessories specially adapted therefor for very small holes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to gas turbine combustors with combustor shingles, wherein the combustor shingles are attached to a supporting structure of the combustion chamber outer walls.
  • the combustion chamber shingles have any (very high, often several thousand) number of Effusionskühllöchern on the side facing the combustion chamber side. These effusion cooling holes serve to cool the shingle from the high temperatures in the combustion chamber.
  • located on the combustion chamber shingle at least one mixing air hole, which serves to air from the outer chamber surrounding the combustion chamber (annulus) in the combustion chamber for the purpose of cooling and Abmagerns combustion and thus the reduction of NOx formation in the combustion chamber conduct.
  • the shingles are often still provided with a ceramic coating, which acts as an insulating layer against the high temperatures in the combustion chamber.
  • shingles are usually carried out either by casting, coating with a ceramic layer and drilling the Effusionskühllöcher (eg with laser) or by casting, drilling and coating or by additive manufacturing processes such as selective laser sintering, direct laser deposition or by electron beam welding.
  • additive manufacturing processes such as selective laser sintering, direct laser deposition or by electron beam welding.
  • the effusion cooling holes are introduced directly into the shingle and the time-consuming drilling is eliminated.
  • Such a substructure has significant disadvantages. It is a) material-intensive, b) it extends the manufacturing process and c) it has to be removed from the shingle after production. This is very expensive. To circumvent this, a horizontal production is often chosen, which has the disadvantage that fewer components can be produced in a manufacturing process, resulting in significantly higher cost per component. Another alternative would be the application of the Zumischlochgeometrie projecting into the combustion chamber in a further step, this is also associated with costs.
  • the invention has for its object to provide a combustion chamber shingle gas turbine of the type mentioned, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability. It is another object of the invention to provide a suitable manufacturing method for such a combustion chamber shingle.
  • the combustion chamber shingle has at least one support element which supports the mixing air hole or the flow guide element (chute) provided there for a vertical production.
  • the support element is preferably provided on one side of the mixing air hole, which is arranged with respect to the flow along the combustion chamber shingles / surface on the side facing away from the flow.
  • the support member may have any shape, but it is designed in a favorable embodiment as a rib whose length and / or thickness of the size and diameter of the mixing air hole or the associated flow guide depends.
  • the number of ribs is arbitrary, as well as their concrete structural design, which can be flow-optimized, for example.
  • the combustion chamber shingle in a vertical arrangement by means of an additive manufacturing process, as known from the prior art, made.
  • the support element is arranged on the downwardly directed side of the admixing hole in order to support the flow guide element (chute) during additive production, in which layered material is applied, and in this way to prevent it from being drawn down during production kinks or is deformed downwards.
  • the support element is arranged exclusively on the side of the mixing air hole or the flow guide element facing away from the flow.
  • the support element is provided with effusion cooling holes in order to ensure good cooling of the combustion chamber shingles during operation.
  • the support element is designed to be smaller than or equal to the diameter of the mixing air hole or the flow guide element.
  • the invention thus makes it possible to produce a combustion chamber shingle with a mixing air hole or flow guide element integrated into the combustion chamber shingle with additive processes in a vertical arrangement of the combustion chamber shingle, whereby enable a significant cost reduction compared to a horizontal production.
  • the savings potential can be up to 50%.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, extending radially inward from the engine casing 21 in an annular flow passage through the compressors 13, 14 protrude.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 schematically shows a combustion chamber 15.
  • the combustion chamber 15 includes a fuel nozzle 29, which is supported in a conventional manner to a combustion chamber head. Furthermore, a combustion chamber outer housing 30 and a combustion chamber inner housing 31 are provided.
  • a combustion chamber wall 32 encloses the actual combustion chamber 15 and carries combustion chamber shingles 34.
  • the reference numeral 33 schematically shows a turbine precursor series. By Zumischlöcher 35 air is supplied in the usual manner. The inflow direction is designated by the reference numeral 36.
  • Fig. 3 shows a known from the prior art combustor shingle 34 in plan view and various side views. It can be seen in particular that the mixing air hole 35 is provided with a tubular flow guiding element projecting. In addition, the combustion chamber shingle 34 has a plurality of effusion cooling holes 37. The flow guide 35 is substantially tubular and beveled with respect to its contour flow optimized.
  • FIG. 11 shows a side view of a prior art manufacturing arrangement in which a combustor shingle 34 is fabricated vertically by additive processes, such as selective laser sintering, direct laser deposition, or electron beam deposition welding.
  • the Effusionskühllöcher 37 can be introduced directly into the combustion chamber shingles 34, so that a subsequent drilling is not required.
  • the Fig. 4 shows a machine bed 41, on which the combustion chamber shingle 34 is arranged vertically.
  • an additional substructure 38 is required, which must be additionally provided, for example in the form of a support beam or the like.
  • the substructure 38 interferes with the additive manufacturing process, entails additional costs and represents an additional auxiliary component which must be handled separately.
  • the Fig. 5 shows an embodiment of the invention, analog Fig. 4 , from which it can be seen that the support of the flow-guiding element 35 with the admixing hole takes place by means of at least one rib-like support element 39, which can be produced first (production direction 40) and which supports the subsequent production of the flow-guiding element 35. This results in the thin wall thicknesses formed in the additive process sufficient stability of the flow guide 35 during manufacture.
  • the Fig. 6 shows an embodiment of a combustion chamber shingle 34 according to the invention, which is provided with three rib-shaped support elements 39. These are on the side of the mixing air hole 35 facing away from the inflow direction 36 provided and each have a small width. The width is dimensioned such that effusion cooling holes 37 can be formed in the support elements 39.
  • Fig. 7 shows a side view in which the support member 39 is not, as in Fig. 6 shown wedge-shaped, but has a rounding and is additionally provided with Effusionskühllöchern 37 which penetrate the support member 39 laterally.
  • the 8 and 9 show alternative embodiments with a plurality of support elements 39, which are dimensioned and arranged differently and are also provided with Effusionskühllöchern 37.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13191946.6A 2012-11-13 2013-11-07 Bardeau de chambre de combustion d'une turbine à gaz et son procédé de fabrication Not-in-force EP2730844B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102012022259.9A DE102012022259A1 (de) 2012-11-13 2012-11-13 Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung

Publications (2)

Publication Number Publication Date
EP2730844A1 true EP2730844A1 (fr) 2014-05-14
EP2730844B1 EP2730844B1 (fr) 2018-04-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13191946.6A Not-in-force EP2730844B1 (fr) 2012-11-13 2013-11-07 Bardeau de chambre de combustion d'une turbine à gaz et son procédé de fabrication

Country Status (3)

Country Link
US (1) US10174947B1 (fr)
EP (1) EP2730844B1 (fr)
DE (1) DE102012022259A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106523158A (zh) * 2016-11-09 2017-03-22 南京航空航天大学 一种涡轴发动机进气装置及操作方法
EP3182011A1 (fr) * 2015-12-16 2017-06-21 Rolls-Royce Deutschland Ltd & Co KG Paroi d'un composant à refroidir à l'aide d'air de refroidissement, en particulier paroi de chambre de combustion de turbine à gaz

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US20210156563A1 (en) * 2019-11-22 2021-05-27 United Technologies Corporation Inspection port for an attritable engine support structure
CN112146127B (zh) * 2020-08-13 2022-04-08 南京航空航天大学 用于调节燃烧室出口温度分布的异型掺混孔
CN116557910A (zh) * 2022-01-27 2023-08-08 通用电气公司 具有交替稀释栅的燃烧器

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GB2113377A (en) * 1982-01-15 1983-08-03 Rolls Royce Improvements in or relating to flame tubes
US4622821A (en) * 1985-01-07 1986-11-18 United Technologies Corporation Combustion liner for a gas turbine engine
EP0481885A1 (fr) * 1990-10-17 1992-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif de refroidissement de la paroi d'une chambre de combustion
DE10214570A1 (de) 2002-04-02 2004-01-15 Rolls-Royce Deutschland Ltd & Co Kg Mischluftloch in Gasturbinenbrennkammer mit Brennkammerschindeln
EP0972992B1 (fr) 1998-07-16 2005-10-12 General Electric Company Chemise de chambre de combustion
GB2444736A (en) * 2006-12-12 2008-06-18 Rolls Royce Plc Combustor wall with air intake port

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FR2674317B1 (fr) * 1991-03-20 1993-05-28 Snecma Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
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FR2714152B1 (fr) * 1993-12-22 1996-01-19 Snecma Dispositif de fixation d'une tuile de protection thermique dans une chambre de combustion.
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Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2113377A (en) * 1982-01-15 1983-08-03 Rolls Royce Improvements in or relating to flame tubes
US4622821A (en) * 1985-01-07 1986-11-18 United Technologies Corporation Combustion liner for a gas turbine engine
EP0481885A1 (fr) * 1990-10-17 1992-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Dispositif de refroidissement de la paroi d'une chambre de combustion
EP0972992B1 (fr) 1998-07-16 2005-10-12 General Electric Company Chemise de chambre de combustion
DE10214570A1 (de) 2002-04-02 2004-01-15 Rolls-Royce Deutschland Ltd & Co Kg Mischluftloch in Gasturbinenbrennkammer mit Brennkammerschindeln
GB2444736A (en) * 2006-12-12 2008-06-18 Rolls Royce Plc Combustor wall with air intake port

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3182011A1 (fr) * 2015-12-16 2017-06-21 Rolls-Royce Deutschland Ltd & Co KG Paroi d'un composant à refroidir à l'aide d'air de refroidissement, en particulier paroi de chambre de combustion de turbine à gaz
US10429069B2 (en) 2015-12-16 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Wall of a structural component, in particular of gas turbine combustion chamber wall, to be cooled by means of cooling air
CN106523158A (zh) * 2016-11-09 2017-03-22 南京航空航天大学 一种涡轴发动机进气装置及操作方法

Also Published As

Publication number Publication date
DE102012022259A1 (de) 2014-05-28
US10174947B1 (en) 2019-01-08
EP2730844B1 (fr) 2018-04-18

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